A Time Sequence Control Method of Switching Magnetic Moment for Microsatellite

Abstract

The invention provides a time-series control method of switching magnetic moments for micro-satellites, comprising the following steps: (1) calculating the three-axis magnetic moment; (2) determining the relationship between the magnetic measurement and magnetic control period and the satellite control period according to the magnetic control accuracy requirements (3) compare and calculate the relationship between the magnetic moment and the maximum output magnetic moment of the switch type magnetic torque device, and determine the time series output of each satellite control cycle; The second magnetic test is completed to complete the time series control input of the switching magnetic moment. The advantage of the present invention is that, according to the magnetic control accuracy requirement, the magnetic measurement and magnetic control cycle on the star is obtained, and the pulse width control is converted into an instruction sequence of whether to output magnetic moments in multiple control cycles in each magnetic measurement and magnetic control cycle, which improves the magnetic The control efficiency is high, and the real-time magnetic control of micro-satellites in orbit is realized.

Description

technical field [0001] The invention relates to the technical field of satellites, in particular to a time-series control method of switching magnetic moments for micro-satellites. Background technique [0002] The attitude control system of a satellite generally consists of a sensor, an actuator, and an attitude control processing unit. In the process of magnetic control of micro-satellites to capture the sun, the switch-type magnetic torque device is used as the satellite actuator for magnetic control, the magnetometer is used as the satellite sensor for magnetic measurement, and the satellite computer is used as the attitude control processing unit for calculation. [0003] The magnetic torquer component is an important executive component of the carbon satellite attitude control subsystem. It is generally formed by a permalloy rod as a magnetic core, and an enameled wire of a certain specification and number of turns is wound on it. The magnetic torque device passes a c...

AI Technical Summary

Problems solved by technology

[0014] The advantage of the present invention is that it provides a time-series control method for the pulse width control deviation of the micro-satellite magnetotorque. Whether multiple control cycles in the magnetic control cycle output the instruction sequence of the magnetic moment solves the problem of time conflicts caused by the lack of time precision of pulse width modulation control and the need for data management of the star computer at the same time, which simplifies the control complexity and improves The efficiency of magnetic control is improved, and the real-time magnetic control of micro-satellites in orbit is realized.

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